DAE-11 AIRFOIL (dae11-il)
DAE-11 AIRFOIL - Drela DAE11 low Reynolds number airfoil
| Details | Dat file | Parser | |
|
(dae11-il) DAE-11 AIRFOIL Drela DAE11 low Reynolds number airfoil Max thickness 12.8% at 32.8% chord. Max camber 6.6% at 44.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DAE-11 AIRFOIL
42.0 40.0
0.0000000 0.0000000
0.0007570 0.0051431
0.0032916 0.0114678
0.0082926 0.0193346
0.0164960 0.0287274
0.0283640 0.0393002
0.0439665 0.0505399
0.0628794 0.0618045
0.0844076 0.0725648
0.1079150 0.0825170
0.1329336 0.0915270
0.1590953 0.0995398
0.1861180 0.1065505
0.2137908 0.1125580
0.2419395 0.1175854
0.2704253 0.1216576
0.2991491 0.1248017
0.3280559 0.1270426
0.3570916 0.1283815
0.3861833 0.1288502
0.4152550 0.1284338
0.4442736 0.1271093
0.4732231 0.1248878
0.5020466 0.1217780
0.5306811 0.1177742
0.5591414 0.1128383
0.5875807 0.1069073
0.6162661 0.0999911
0.6454374 0.0922048
0.6752228 0.0837204
0.7056532 0.0747378
0.7366037 0.0655023
0.7673512 0.0564167
0.7977796 0.0476052
0.8279501 0.0391518
0.8579515 0.0311284
0.8879669 0.0235641
0.9186085 0.0163798
0.9478748 0.0100446
0.9700075 0.0056151
0.9864834 0.0025379
1.0000000 -.0000000
0.0000000 0.0000000
0.0004919 -.0034860
0.0020116 -.0064284
0.0044148 -.0087908
0.0080862 -.0107002
0.0141149 -.0123747
0.0245731 -.0138784
0.0414512 -.0148893
0.0648951 -.0150664
0.0926077 -.0144625
0.1225845 -.0132928
0.1536785 -.0117470
0.1853836 -.0099672
0.2174497 -.0080524
0.2497389 -.0060686
0.2821721 -.0040608
0.3146113 -.0020681
0.3469645 -.0001193
0.3792396 0.0017525
0.4114338 0.0035362
0.4435539 0.0052000
0.4756050 0.0067337
0.5075752 0.0081154
0.5394692 0.0093041
0.5713123 0.0102848
0.6031123 0.0110455
0.6348824 0.0115701
0.6666354 0.0118657
0.6983765 0.0119312
0.7301015 0.0117728
0.7617894 0.0113933
0.7934214 0.0107738
0.8249984 0.0099002
0.8565623 0.0087586
0.8883292 0.0073310
0.9200152 0.0056143
0.9479936 0.0038679
0.9696512 0.0023497
0.9862833 0.0010768
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for DAE-11 AIRFOIL (dae11-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dae11-il | 50,000 | 9 | 6.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 50,000 | 5 | 13.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 100,000 | 9 | 31.3 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 100,000 | 5 | 32.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 200,000 | 9 | 79 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 200,000 | 5 | 83.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 500,000 | 9 | 135.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 500,000 | 5 | 132.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 1,000,000 | 9 | 177.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 1,000,000 | 5 | 165 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||